IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE

• US 20120234012A1
• Filed: 03/15/2011
• Published: 09/20/2012
• Est. Priority Date: 03/15/2011
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Chila, Ronald James, Melton, Patrick Benedict, DeForest, Russell, Cihlar, David William, Brown, Jerome David
• Granted Patent: US 8,887,508 B2
• Time in Patent Office: Days
• US Class Current: 60/752
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: Y10T 29/49229 Prime mover or fluid pump making

Abstract

An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.

Claims

1. A method for forming an impingement sleeve, the method comprising:

designing a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern configured to provide a desired operational value for a transition piece; and

manufacturing an impingement sleeve, the impingement sleeve defining the plurality of cooling holes having the cooling hole pattern.

2. The method of claim 1, wherein the designing step comprises determining a heat flux of the transition piece.

3. The method of claim 1, wherein the designing step comprises determining the desired operational value.

4. The method of claim 1, wherein the desired operational value is at least one of a generally uniform low cycle fatigue value, an average low cycle fatigue value, a generally uniform temperature, an average temperature, a generally uniform strain, an average strain, a generally uniform cooling value, an average cooling value, a generally uniform thermal barrier coating temperature, or an average thermal barrier coating temperature.

5. The method of claim 1, wherein the designing step comprises:

inputting a combustor characteristic into a processor; and

utilizing the combustor characteristic in the processor to determine the cooling hole pattern.

6. The method of claim 5, wherein the combustor characteristic is at least one of hot gas temperature, working fluid temperature, transition piece stress, transition piece strain, transition piece material, impingement sleeve geometry, spacing between impingement sleeve and transition piece, number of cooling holes, number of cooling hole sizes, cooling hole sizes, or total area of cooling holes.

7. The method of claim 1, wherein the designing step comprises determining a required cooling mode for the desired operational value.

8. The method of claim 1, wherein the designing step comprises partitioning the transition piece into a plurality of segments, wherein the cooling hole pattern is designed for the impingement sleeve with respect to each of the plurality of segments.

9. A method for designing an impingement sleeve, the method comprising:

determining a desired operational value for a transition piece;

inputting a combustor characteristic into a processor; and

utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.

10. The method of claim 9, further comprising determining a heat flux of the transition piece.

11. The method of claim 9, wherein the desired operational value is at least one of a generally uniform low cycle fatigue value, an average low cycle fatigue value, a generally uniform temperature, an average temperature, a generally uniform strain, an average strain, a generally uniform cooling value, an average cooling value, a generally uniform thermal barrier coating temperature, or an average thermal barrier coating temperature.

12. The method of claim 9, wherein the combustor characteristic is at least one of hot gas temperature, working fluid temperature, transition piece stress, transition piece strain, transition piece material, impingement sleeve geometry, spacing between impingement sleeve and transition piece, number of cooling holes, number of cooling hole sizes, cooling hole sizes, or total area of cooling holes.

13. The method of claim 9, further comprising determining a required cooling mode for the desired operational value.

14. The method of claim 9, further comprising partitioning the transition piece into a plurality of segments, wherein a cooling hole pattern is determined for the impingement sleeve with respect to each of the plurality of segments.

15. The method of claim 9, further comprising determining a plurality of desired operational values.

16. The method of claim 9, further comprising inputting a plurality of combustor characteristics.

17. An impingement sleeve for a combustor, comprising:

a body configured to at least partially surround a transition piece of the combustor; and

a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece,

wherein at least a portion of the plurality of cooling holes are generally longitudinally asymmetric.

18. The impingement sleeve of claim 17, wherein the desired operational value is at least one of a generally uniform low cycle fatigue value, an average low cycle fatigue value, a generally uniform temperature, an average temperature, a generally uniform strain, an average strain, a generally uniform cooling value, an average cooling value, a generally uniform thermal barrier coating temperature, or an average thermal barrier coating temperature.

19. The impingement sleeve of claim 17, wherein the cooling hole pattern is designed by determining the desired operational value for the transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine the cooling hole pattern for the impingement sleeve.

20. The impingement sleeve of claim 19, wherein the combustor characteristic is at least one of hot gas temperature, working fluid temperature, transition piece stress, transition piece strain, transition piece material, impingement sleeve geometry, spacing between impingement sleeve and transition piece, number of cooling holes, number of cooling hole sizes, cooling hole sizes, or total area of cooling holes.